EP1882885A2 - Chemise en céramique pour moteur de turbine à gaz - Google Patents

Chemise en céramique pour moteur de turbine à gaz Download PDF

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Publication number
EP1882885A2
EP1882885A2 EP07252052A EP07252052A EP1882885A2 EP 1882885 A2 EP1882885 A2 EP 1882885A2 EP 07252052 A EP07252052 A EP 07252052A EP 07252052 A EP07252052 A EP 07252052A EP 1882885 A2 EP1882885 A2 EP 1882885A2
Authority
EP
European Patent Office
Prior art keywords
combustor
recited
combustor section
ceramic
support
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07252052A
Other languages
German (de)
English (en)
Other versions
EP1882885B1 (fr
EP1882885A3 (fr
Inventor
Jun Shi
Jason Lawrence
David J. Bombara
Richard S. Tuthill
Jeffrey D. Melman
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP1882885A2 publication Critical patent/EP1882885A2/fr
Publication of EP1882885A3 publication Critical patent/EP1882885A3/fr
Application granted granted Critical
Publication of EP1882885B1 publication Critical patent/EP1882885B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05002—Means for accommodate thermal expansion of the wall liner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • This invention relates to gas turbine engines and, more particularly, to a combustor assembly having a unique attachment between a ceramic combustor can and a metal fuel-air mixture section.
  • Conventional gas turbine engines such as those used in aircraft, utilize a combustor to ignite a mixture of fuel and compressed air. Utilizing significant compressed air may further reduce the air available for combustor liner cooling and result in pressure loss during the cooling of the combustor liner. Such a lean mixture reduces the amount of air available to cool the combustor and increases the combustor temperature.
  • Common by-products of fuel combustion are NOx and CO. To reduce NOx produced in the combustor, it is desirable to reduce the flame temperature. This requires a high percentage of compressed air to be mixed with the fuel to produce a lean fuel air mixture. For combustors made entirely of metal, the increase in temperature may exceed a desirable operating temperature of the metal.
  • CTE coefficient of thermal expansion
  • the present invention from one aspect includes within its scope a combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween.
  • An air fuel mixer and an igniter are mounted to the support assembly such that the ceramic combustor can receive the ignition products of the ignited fuel and air mixture.
  • One support assembly includes a metal front support ring which interfaces with the ceramic combustor can.
  • An inclined contact interface permits the front support ring to slide relative the ceramic combustor can upon thermal excursion.
  • a relatively thin wall thickness front support ring in combination with slots truncate hoop stress.
  • a multitude of fasteners provide definitive circumferential and axial constraints between the front support ring and the ceramic combustor can.
  • Fastener openings through the front support ring are at least partially elliptical or slot-like to facilitate relative sliding between the front support ring and the ceramic combustor can during thermal excursion.
  • Another support assembly includes a heat shield actively cooled by impingement cooling air on the outer diameter thereof.
  • the front support ring As the front support ring now operates in a relatively lower temperature regime since it is protected by the heat shield, the front support ring is able to withstand higher stresses and deform elastically to ensure the safe operation of the ceramic combustor can and the gas turbine engine.
  • Another combustor assembly includes a ceramic combustor can manufactured as a relatively straight cylinder.
  • An axially extended front support ring extends downstream to also support the combustor igniter and includes a reduced diameter stepped interface over which the ceramic combustor can is fitted.
  • Another combustor assembly includes a ceramic combustor can with an outwardly flared outer diameter interface to receive an extended heat shield and an attached front support ring.
  • the extended heat shield is welded or otherwise affixed to the front support ring to form a radial spring interface with the outwardly flared outer diameter interface to readily accommodate thermal expansion.
  • Another combustor assembly includes a ceramic combustor can with a reduced diameter attachment segment to provide a bottle-shaped ceramic combustor can.
  • the ceramic combustor can is sandwiched between an outer-segmented ring and an inner full ring.
  • the segmentation and fasteners per segment permit the outer segmented ring to follow the thermal growth of the ceramic combustor can without significant stress.
  • Another support assembly includes a multitude of springs formed of "U" shaped metal strips that receive a front lip of the ceramic combustor can between an inner support and an outer support plate.
  • a fastener through each spring pins" the ceramic combustor can axially and circumferentially, while the springs provide radial support.
  • Another support assembly confines thermal growth mismatch within a plane normal to a longitudinal axis of the ceramic combustor can.
  • Another combustor assembly includes a ceramic combustor can manufactured as a relatively straight cylinder with a frustro-conical attachment segment.
  • the frustro-conical attachment segment facilitates sliding of the ceramic combustor can between an inner frustro-conical support and a segmented outer frustro-conical support.
  • the present invention therefore provides a combustor assembly that maintains a tight fit between a ceramic combustor can and a metal support assembly over a relatively wide temperature range.
  • FIG. 1 illustrates selected portions of a combustor section 10 used, for example, in a gas turbine engine.
  • the combustor section 10 includes an air fuel mixer 12 that supplies a mixture of air and fuel to be ignited by an igniter 14.
  • the air fuel mixer 12 and the igniter 14 are mounted to a support assembly 16 preferably manufactured of metallic materials.
  • the support assembly 16 is secured to a ceramic combustor can 18, which receives the ignition products of the ignited fuel and air mixture.
  • the ceramic combustor can 18 is preferably mounted within a combustor outer casing 20 and inner casing 22.
  • the ceramic combustor can 18 directs the ignition products through a transition duct 24 and into a turbine section (not shown) of a gas turbine engine.
  • a flame temperature distribution in the combustion section 10 is such that the front end near the igniter 14 has a relatively low temperature flame and the aft end near the ceramic can 18 and transition duct 24 has a relatively high temperature flame.
  • Utilizing the support assembly 16 near the relatively cooler flame and the ceramic can 18 near the relatively hotter flame provides the benefit of reducing undesirable carbon monoxide emissions produced in previously known combustor assemblies.
  • the ceramic material of the ceramic can 18 does not require as much cooling as a metal material. Since there is less cooling with the ceramic can 18, less carbon monoxide is produced compared to previously known combustor assemblies that utilize a metallic can. Further, the ceramic material of the ceramic can 18 is less dense than metal and therefore reduces the weight of the gas turbine engine within which the combustor section 10 is mounted. Furthermore, utilizing the relatively inexpensive (compared to ceramic sections) metal support assembly 16 near the cooler flame portion reduces the expense of the combustion section 10.
  • a support assembly 16A includes a metal front support ring 30 to interface with the ceramic combustor can 18.
  • the metal front support ring 30 may grow radially more than the ceramic combustor can 18.
  • An inclined contact interface 31 defined by the front support ring 30 permits the support assembly 16A to slide relative the ceramic combustor can 18 upon thermal excursion. Sliding alleviates thermal growth incompatibility and therefore minimizes thermal stress.
  • a preset gap is preferably provided such that the front support ring 30 can grow thermally free from interfering with the ceramic can 18 and therefore avoid thermally induced stresses.
  • a multitude of fasteners 34 provide circumferential and axial constraints between the front support ring 30 and the ceramic combustor can 18.
  • the fasteners 34 are preferably manufactured of high temperature alloys with a center passage 36 (Figure 2C) to pass cooling air.
  • Fastener openings 38 through the inclined contact interface 31 are preferably at least partially elliptical, slot-like or sized ( Figure 2C) to facilitate relative movement between the front support ring 30 and the ceramic combustor can 18 during thermal excursion.
  • the front support ring 30 of Figures 2A-2C is directly exposed to hot combustion gas. Although effective, the integrity of the front support ring 30 may be affected over a prolonged time period since the ceramic combustor can 18 reduces cooling on one side thereof. To provide further integrity, a heat shield 40 is preferably additionally incorporated radially inboard of the metal front support ring 30 (Figure 3A).
  • another support assembly 16B includes the heat shield 40 which is welded or otherwise mounted to the front support ring 30.
  • the heat shield 40 is actively cooled by impingement cooling air on the outer diameter thereof.
  • front support ring 30 will withstand higher stresses.
  • the ceramic combustor can 18A is manufactured as a relatively straight cylinder.
  • a support assembly 16C includes an axially extended front support ring 42 which extends downstream to support the ceramic combustor can.
  • a gap relative the ceramic combustor can 18A, the relatively thin material, a multitude of slots 44, and the elongated fastener opening 46 as also described above sufficiently accommodates thermal stress.
  • the extended front support ring 42 includes a reduced diameter stepped interface 48 ( Figure 4B) over which the ceramic combustor can 18A is received.
  • a ceramic combustor can 18B includes an outwardly flared attachment segment 48 to receive an extended heat shield 50 and an attached front support ring 52 (Figure 5B) of a support assembly 16D.
  • the front support ring 52 preferably includes slots 58 as described above to truncate hoop stresses.
  • the extended heat shield 50 is preferably welded or otherwise affixed to the front support ring 52 to form a radial spring interface with the outwardly flared attachment segment 48. That is, the attached front support ring 52 is essentially radially interference fit into the outwardly flared attachment segment 48 and axially retained therein by a multitude of fasteners 54 which may be mounted through elongated openings 56. Thermal expansion is thereby readily accommodated.
  • a ceramic combustor can 18C with a reduced diameter attachment segment 60 provides a bottle-shaped ceramic combustor can 18C.
  • combustors where the majority of the combustion process takes place close to the fuel air mixer 12, a significant amount of CO is generated at the forward portion of the combustor and subsequently quenched.
  • One attribute of this design is that the attachment segment 60 is in a relatively low temperature part of the combustor, which enables thermal stress management by minimizing the overall thermal growth.
  • the ceramic combustor can 18C attachment segment 60 is sandwiched between an outer-segmented ring 62 and an inner full ring 64 (Figure 6C). Thermal stress is received primarily through the complaint inner full ring 64 and the separated sections 66 of the outer-segmented ring 62.
  • the outer segmented ring 62 may be formed into a multiple of segments (three shown 66A, 66B, 66C, each with two fasteners 68; Figure 6B). The segmentation and the fasteners per segment permit the outer segmented ring 62 to follow the thermal growth of the ceramic combustor can 18C without significant stress.
  • the inner full ring 64 preferably includes a ridge 70 which seals to the ceramic combustor can 18C in an interference manner irrespective of relative thermal distortion (Figure 6C). Another attribute is that the inner full ring 64 includes a frustro-conical surface 72 that defines a cooling path about the fuel air mixer 12.
  • a multitude of retainers 74 preferably formed of "U" shaped metal strips that receive a front lip of the ceramic combustor can 18C between an inner support 78 and an outer support plate 80.
  • a fastener 76 through each retainer 74 "locks” the ceramic combustor can 18C axially and circumferentially, while the retainers 74 provide radial support ( Figures 7B and 7C).
  • a gap is preferably formed between a radially inboard leg 741 of the retainer 74 and the ceramic combustor can 18C.
  • the OD of the ceramic combustor can 18C is piloted on the ID of each radially outboard leg 74U of the retainer 74.
  • Both legs 741, 74U behave like a beam upon loading and as such they deform substantially without inducing high stresses to accommodate temperature excursion of the ceramic combustor can 18C ( Figure 7D).
  • the retainers 74 are attached to the outer support plate 80 by the fasteners 82 ( Figure 7C).
  • the outer support plate 80 may preferably include an extension 83 which facilitates attachment to the combustor outer casing 20 and inner casing 22 ( Figure 1).
  • thermal growth mismatch is confined within a plane normal to a longitudinal axis A of the ceramic combustor can 18D.
  • the ceramic combustor can 18D includes a formed radial flange 84. Although relatively more complicated to manufacture, the ceramic combustor can 18D facilitates an uncomplicated interface with the air fuel mixer 12. As such, radial thermal growth incompatibility need only be resolved within a plane that contains the radial flange 84.
  • a support assembly 16G includes a metal support plate 86, a metal inner support 88, an attachment member 87 and a multitude of fasteners 90 (Figure 8B).
  • the metal inner support 88 includes a multiple of fingers 92 which generally operate as a spring to provide an interference fit with the ceramic combustor can 18D.
  • the support plate 86 includes a multiple of elongated fastener opening 94 (Figure 8C).
  • the openings 94 are sized in such a way that after assembly and at room temperature, the fasteners 90 are located at the radially outer positions (Figure 8C).
  • the metal support plate 86 grows more than the ceramic combustor can 18D and the fasteners 90 are located at radial inward positions of the openings 94.
  • the ceramic combustor can 18D is clamped to the stiff metal support plate 86 with the fasteners 90 and an associated spring washer 96 such as Bellville washers.
  • the fingers 92 maintain the a retention load during cold to hot thermal excursions to provide a friction force that permits the metal support plate 86 to slide relative the ceramic combustor can 18D while the spring washers 96 maintain tension on the fasteners 90 during radial movement.
  • a ceramic combustor can 18E is manufactured as a relatively straight cylinder with a frustro-conical attachment segment 98 which is preferably of an approximately 45 degree slope.
  • the frustro-conical attachment segment 98 facilitates sliding of the ceramic combustor can 18E between an inner frustro-conical support 100 and a segmented outer frustro-conical support 102 (Figure 9B).
  • the segmented outer frustro-conical support 102 may be formed into a multiple of segments (three shown 104A, 104B, 104C; each with two fasteners 106).
  • segmentation and the fasteners per segment permit the segmented outer frustro-conical support 102 to follow the thermal growth of the ceramic combustor can 18D without significant stress during temperature transient and therefore reduces thermal stress buildup as afore mentioned.
  • a multiple of slots 105, 110 in each of the inner frustro-conical support 100 and a segmented outer frustro-conical support 102 operate in accordance with that described above. It should be understood that the inner frustro-conical support 100 is received within the ceramic combustor can 18D from the end opposite the frustro-conical attachment segment 98 such that fasteners 106 in the segmented outer frustro-conical support 102 are received therein so as to clamp the ceramic combustor can 18D therebetween ( Figure 9C).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
EP07252052.1A 2006-07-27 2007-05-18 Chemise en céramique pour moteur de turbine à gaz Expired - Fee Related EP1882885B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/494,083 US8863528B2 (en) 2006-07-27 2006-07-27 Ceramic combustor can for a gas turbine engine

Publications (3)

Publication Number Publication Date
EP1882885A2 true EP1882885A2 (fr) 2008-01-30
EP1882885A3 EP1882885A3 (fr) 2011-10-26
EP1882885B1 EP1882885B1 (fr) 2014-09-03

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EP07252052.1A Expired - Fee Related EP1882885B1 (fr) 2006-07-27 2007-05-18 Chemise en céramique pour moteur de turbine à gaz

Country Status (3)

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US (1) US8863528B2 (fr)
EP (1) EP1882885B1 (fr)
JP (1) JP2008032379A (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012156186A1 (fr) * 2011-05-16 2012-11-22 Siemens Aktiengesellschaft Plaque de montage de brûleur vissée côté chambre de combustion
WO2013028169A1 (fr) 2011-08-22 2013-02-28 Majed Toqan Chambre de combustion tubo-annulaire dotée de buses d'air et de combustible tangentielles destinées à être utilisées sur des moteurs de turbine à gaz
WO2013028167A2 (fr) 2011-08-22 2013-02-28 Majed Toqan Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz
WO2013144048A1 (fr) * 2012-03-29 2013-10-03 Alstom Technology Ltd Chambre de combustion de turbine à gaz
FR2998039A1 (fr) * 2012-11-09 2014-05-16 Snecma Chambre de combustion pour une turbomachine
FR3017928A1 (fr) * 2014-02-27 2015-08-28 Snecma Turbomachine a bride externe de chambre de combustion de type "sandwich"
GB2564913A (en) * 2017-07-21 2019-01-30 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
US10422532B2 (en) 2013-08-01 2019-09-24 United Technologies Corporation Attachment scheme for a ceramic bulkhead panel
EP3640543A1 (fr) * 2018-10-15 2020-04-22 United Technologies Corporation Ensemble de fixation de chemise de chambre de combustion pour moteur à turbine à gaz
US10712008B2 (en) 2016-10-13 2020-07-14 Rolls-Royce Plc Combustion chamber and a combustion chamber fuel injector seal
US11293637B2 (en) 2018-10-15 2022-04-05 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2932251B1 (fr) * 2008-06-10 2011-09-16 Snecma Chambre de combustion de moteur a turbine a gaz comportant des deflecteurs en cmc
JP5888973B2 (ja) * 2011-12-22 2016-03-22 三菱日立パワーシステムズ株式会社 ガスタービンの燃焼器
EP3087322B1 (fr) * 2013-12-23 2019-04-03 General Electric Company Injecteur de carburant doté de structures de support souples
FR3017693B1 (fr) * 2014-02-19 2019-07-26 Safran Helicopter Engines Chambre de combustion de turbomachine
US10760451B2 (en) * 2015-05-22 2020-09-01 General Electric Company Manufacture and installation of diffuser flow mixing lobes
US10648669B2 (en) * 2015-08-21 2020-05-12 Rolls-Royce Corporation Case and liner arrangement for a combustor
US10197278B2 (en) * 2015-09-02 2019-02-05 General Electric Company Combustor assembly for a turbine engine
US10378771B2 (en) 2016-02-25 2019-08-13 General Electric Company Combustor assembly
US10281153B2 (en) * 2016-02-25 2019-05-07 General Electric Company Combustor assembly
US10215039B2 (en) 2016-07-12 2019-02-26 Siemens Energy, Inc. Ducting arrangement with a ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2140401C3 (de) * 1971-08-12 1979-12-06 Lucas Industries Ltd., Birmingham (Grossbritannien) Flammrohr für Gasturbinen
US3911672A (en) * 1974-04-05 1975-10-14 Gen Motors Corp Combustor with ceramic liner
US4363208A (en) 1980-11-10 1982-12-14 General Motors Corporation Ceramic combustor mounting
US4573320A (en) 1985-05-03 1986-03-04 Mechanical Technology Incorporated Combustion system
JPH0279578A (ja) 1988-09-14 1990-03-20 Sony Corp ビームインデックス形カラーテレビジョン受像機
GB9108235D0 (en) * 1991-04-17 1991-06-05 Rolls Royce Plc A combustion chamber assembly
US5457954A (en) * 1993-12-21 1995-10-17 Solar Turbines Inc Rolling contact mounting arrangement for a ceramic combustor
US5392596A (en) 1993-12-21 1995-02-28 Solar Turbines Incorporated Combustor assembly construction
US6182451B1 (en) * 1994-09-14 2001-02-06 Alliedsignal Inc. Gas turbine combustor waving ceramic combustor cans and an annular metallic combustor
JPH08312962A (ja) * 1995-05-16 1996-11-26 Nissan Motor Co Ltd ガスタービンの燃焼器
JPH08312963A (ja) * 1995-05-19 1996-11-26 Nissan Motor Co Ltd ガスタービンの燃焼器
JPH0979578A (ja) * 1995-09-11 1997-03-28 Nissan Motor Co Ltd ガスタービンの燃焼器
US6047539A (en) * 1998-04-30 2000-04-11 General Electric Company Method of protecting gas turbine combustor components against water erosion and hot corrosion
JP3478531B2 (ja) * 2000-04-21 2003-12-15 川崎重工業株式会社 ガスタービンのセラミック部品支持構造
US6397603B1 (en) 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner
WO2002088601A1 (fr) * 2001-04-27 2002-11-07 Siemens Aktiengesellschaft Chambre de combustion, en particulier d'une turbine a gaz
FR2825781B1 (fr) * 2001-06-06 2004-02-06 Snecma Moteurs Montage elastique de chambre ce combustion cmc de turbomachine dans un carter metallique
FR2825783B1 (fr) * 2001-06-06 2003-11-07 Snecma Moteurs Accrochage de chambre de combustion cmc de turbomachine par pattes brasees
US7104066B2 (en) * 2003-08-19 2006-09-12 General Electric Company Combuster swirler assembly
FR2871847B1 (fr) * 2004-06-17 2006-09-29 Snecma Moteurs Sa Montage d'un distributeur de turbine sur une chambre de combustion a parois en cmc dans une turbine a gaz
US7237389B2 (en) * 2004-11-18 2007-07-03 Siemens Power Generation, Inc. Attachment system for ceramic combustor liner
US7647779B2 (en) 2005-04-27 2010-01-19 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012156186A1 (fr) * 2011-05-16 2012-11-22 Siemens Aktiengesellschaft Plaque de montage de brûleur vissée côté chambre de combustion
CN104053883B (zh) * 2011-08-22 2017-02-15 马吉德·托甘 混合用于在燃气涡轮发动机内燃烧的燃烧反应物的方法
WO2013028169A1 (fr) 2011-08-22 2013-02-28 Majed Toqan Chambre de combustion tubo-annulaire dotée de buses d'air et de combustible tangentielles destinées à être utilisées sur des moteurs de turbine à gaz
WO2013028167A2 (fr) 2011-08-22 2013-02-28 Majed Toqan Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz
CN104053883A (zh) * 2011-08-22 2014-09-17 马吉德·托甘 在燃气轮机上使用的具有预混合切向燃料-空气喷嘴的筒状环形燃烧室
EP2748443A4 (fr) * 2011-08-22 2015-05-27 Majed Toqan Chambre de combustion tubo-annulaire dotée de buses d'air et de combustible tangentielles destinées à être utilisées sur des moteurs de turbine à gaz
EP2748444A4 (fr) * 2011-08-22 2015-05-27 Majed Toqan Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz
WO2013144048A1 (fr) * 2012-03-29 2013-10-03 Alstom Technology Ltd Chambre de combustion de turbine à gaz
FR2998039A1 (fr) * 2012-11-09 2014-05-16 Snecma Chambre de combustion pour une turbomachine
US10422532B2 (en) 2013-08-01 2019-09-24 United Technologies Corporation Attachment scheme for a ceramic bulkhead panel
US9988982B2 (en) 2014-02-27 2018-06-05 Snecma Turbine engine with a combustion chamber outer flange of sandwich type
FR3017928A1 (fr) * 2014-02-27 2015-08-28 Snecma Turbomachine a bride externe de chambre de combustion de type "sandwich"
US10712008B2 (en) 2016-10-13 2020-07-14 Rolls-Royce Plc Combustion chamber and a combustion chamber fuel injector seal
GB2564913A (en) * 2017-07-21 2019-01-30 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
EP3640543A1 (fr) * 2018-10-15 2020-04-22 United Technologies Corporation Ensemble de fixation de chemise de chambre de combustion pour moteur à turbine à gaz
US11255547B2 (en) 2018-10-15 2022-02-22 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
US11293637B2 (en) 2018-10-15 2022-04-05 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine

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US20140190167A1 (en) 2014-07-10
JP2008032379A (ja) 2008-02-14
US8863528B2 (en) 2014-10-21
EP1882885B1 (fr) 2014-09-03
EP1882885A3 (fr) 2011-10-26

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